A novel approximate finite-time convergent guidance law with actuator fault

Wang, Wei; Ji, Yi; Lin, Defu; Shi, Zhongjiao; Lin, Shiyao

doi:10.1007/s10586-017-1114-y

Cited by 7 publications

(11 citation statements)

References 27 publications

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“…According to the work in [46], the three-dimensional (3D) homing guidance geometry is shown as Fig. 1, where r denotes the LOS distance between the missile and the target,  and  represent the pitch and azimuth of the LOS angles, respectively.…”

Section: A Engagement Kinematicsmentioning

confidence: 99%

“…In [43], finite time convergence is defined as follow, Lemma 1 (See [46]). Considering the nonlinear system…”

Section: A Design Of a Multi-variable Adaptive Sta-like Guidance Lawmentioning

confidence: 99%

“…To further verify the effectiveness of the proposed guidance law, a FTC guidance law in [46] and a novel transformed PNG law [50] are used as comparison, which can provide reasonable acceleration control command. In order to indicate results of the guidance law, two engagement cases are studied here, and the performance of impact angle constraint are tested as well.…”

Section: Comparion With Other Guidance Lawsmentioning

confidence: 99%

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Impact Angle Constraint Dual-Layer Adaptive Guidance Law With Actuator Faults

Niu

et al. 2020

IEEE Access

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To intercept maneuvering target considering impact angle constraint and actuator faults, a novel three-dimensional (3D) guidance law is proposed in this paper. To guarantee the interception, the multi-variable super-twisting-algorithm-like (STA-like) is adopted in the proposed guidance law, so as to drive the line-of-sight (LOS) angle to the desired value and its rate to zero in finite time in both pitch and azimuth directions. However, it is usually a difficult task for STA-like to select the proper design parameters, and the necessary disturbance gradient for STA-like is also not clearly known, owing to realistic actuator faults and the independence between missile and target. Moreover, the actuator faults in this paper are formulated as disturbances in the control scheme, and the necessary disturbance gradient for STA-like is not clearly known as well. To solve these problems, a multi-variable dual-layer adaptive scheme is employed to adjust the control gains and guarantees its precision. The theoretical analysis and numerical simulation results demonstrate the effectiveness of the proposed guidance law. The combination of STA-like and adaptive theory in the presented guidance law for the first time can guarantee the successful interception and can generate precise and robust control signal simultaneously with impact angle constraint and actuator faults consideration.

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Section: A Engagement Kinematicsmentioning

confidence: 99%

“…In [43], finite time convergence is defined as follow, Lemma 1 (See [46]). Considering the nonlinear system…”

Section: A Design Of a Multi-variable Adaptive Sta-like Guidance Lawmentioning

confidence: 99%

Section: Comparion With Other Guidance Lawsmentioning

confidence: 99%

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Impact Angle Constraint Dual-Layer Adaptive Guidance Law With Actuator Faults

Niu

et al. 2020

IEEE Access

Self Cite

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“…With the characteristics of strong robustness, high precision and no chattering, the well-known super twisting algorithm (STA) [40][41] is a unique continuous second-order SMC and applied in various fields. Compared with other chatteringfree sliding mode control algorithms (higher-order sliding mode for example), STA requires no information about higher-order derivatives.…”

Section: Adaptive Dual-layer Multi-variable Stl Guidance Schemementioning

confidence: 99%

Velocity-Free Fault-Tolerant Rendezvous Law Based on Dual-Layer Adaptive Algorithm

Wang

Shi

et al. 2020

IEEE Access

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Considering the scenario that the obstinate and difficult-repaired sensor and actuator failure always occurs during the spacecraft rendezvous guidance phase and may cause terrible performance, this paper studies the fault-tolerant guidance method and proposes a velocity-free guidance algorithm. Above guidance law is based on a dual-layer adaptive multi-variable super-twisting-like algorithm, where two waving gains are introduced to autonomously adjust the system trajectory subject to the relative velocity. Hence, the complex parameter selection problem is overcome. Moreover, to overcome the sensor fault in relative-velocity channel, a robust observer which can drive the velocity error converge to zero in a small finite time is presented. To test the effectiveness and stability of the proposed guidance law, considering actuator faults, second-order dynamics and saturation, numerical simulations including comparisons and Monte-Carlo are carried out and the results demonstrate above properties.

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“…The aforementioned control systems are known as fault-tolerant control systems (FTCS) (Blanke, 1999). In some references, faults such as actuator fault (Fei et al, 2014; Wang et al, 2019; Zhu et al, 2011), sensor fault (Tan et al, 2019) and loss of the guidance command fault (Chen et al, 2019) are considered in the design of the IGC. However, to the best of our knowledge, no results on the design of IGC laws have been published in the presence of fin failure.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fin failures tolerant integrated guidance and control based on backstepping sliding mode

Ashrafifar

Jegarkandi

2020

Transactions of the Institute of Measurement and Control

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An integrated guidance and control (IGC) is designed in this study for a surface-to-air missile considering burned or broken fin as a fault. The IGC model in the pitch plane is developed with various uncertainties in the presence of fin failure. The considered fault may cause a change in the vehicle’s shape that leads to a change in aerodynamic coefficients and consequently in the model. To identify the new model, aerodynamic coefficients are estimated using an estimator and the result is sent to the controller. Then, an adaptive robust controller is designed using the combination of backstepping and sliding mode scheme to compensate fin failure and changes in the dynamic. The simulation results show the capability of the proposed approach, not only in normal condition but also while a part of the missile’s fin is destroyed.

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A novel approximate finite-time convergent guidance law with actuator fault

Cited by 7 publications

References 27 publications

Impact Angle Constraint Dual-Layer Adaptive Guidance Law With Actuator Faults

Impact Angle Constraint Dual-Layer Adaptive Guidance Law With Actuator Faults

Velocity-Free Fault-Tolerant Rendezvous Law Based on Dual-Layer Adaptive Algorithm

Adaptive fin failures tolerant integrated guidance and control based on backstepping sliding mode

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